EP3351739B1 - Dichtungsstruktur und verfahren zur herstellung davon - Google Patents

Dichtungsstruktur und verfahren zur herstellung davon Download PDF

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Publication number
EP3351739B1
EP3351739B1 EP18151761.6A EP18151761A EP3351739B1 EP 3351739 B1 EP3351739 B1 EP 3351739B1 EP 18151761 A EP18151761 A EP 18151761A EP 3351739 B1 EP3351739 B1 EP 3351739B1
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EP
European Patent Office
Prior art keywords
sealing element
radially inwardly
abradable
surface region
inwardly facing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP18151761.6A
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English (en)
French (fr)
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EP3351739A1 (de
Inventor
Gary Wright
Simon Donovan
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
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Rolls Royce PLC
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Publication date
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Publication of EP3351739A1 publication Critical patent/EP3351739A1/de
Application granted granted Critical
Publication of EP3351739B1 publication Critical patent/EP3351739B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/25—Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/34—Laser welding for purposes other than joining
    • B23K26/342—Build-up welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y10/00—Processes of additive manufacturing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y30/00—Apparatus for additive manufacturing; Details thereof or accessories therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/40—Structures for supporting workpieces or articles during manufacture and removed afterwards
    • B22F10/47—Structures for supporting workpieces or articles during manufacture and removed afterwards characterised by structural features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F2005/005—Article surface comprising protrusions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/234—Laser welding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Definitions

  • the present disclosure relates to a sealing element for positioning radially outwardly of the aerofoil blades of a gas turbine engine, together with a method of manufacturing the same.
  • a sealing structure which may comprise an annular seal or a seal segment ring made up of a plurality of arc shaped seal segments.
  • the turbine blades expand and contract as their temperatures vary and centrifugal loads are imposed upon them. As a consequence, it is normal to provide a small clearance between the turbine blade tips and the seal surface, in order to allow for this variation in blade length.
  • abradable seals for sealing between the turbine blade tips and the sealing structure. This enables the tips of the turbine blades to wear away the seal to an optimum size and shape without causing damage to the turbine blade tips.
  • abradable seals may consist of an open cell foil honeycomb which is brazed in place and subsequently filled with a suitable abradable material, such as a metallic powder.
  • EDM electro discharge machining
  • a sealing segment made from an oxidation resistant alloy to form a honeycomb structure that is also filled with a suitable abradable material, such as a metallic powder.
  • the honeycomb acts as a support for the abradable material. The supporting honeycomb is subsequently partially worn away by the rotating turbine blades, thus forming a seal.
  • the seals may suffer from progressive oxidation attack if the foil material has inadequate oxidation resistance.
  • problems may be experienced with the brazed joints, and the seals may be difficult to cool.
  • EP 3 002 417 A1 discloses a sealing element for positioning radially outwardly of aerofoil blades of a gas turbine engine.
  • a radially inner surface region of the sealing element includes a seal structure having one or more inwardly projecting walls formed by additive layer, powder fed, laser weld deposition.
  • the walls form a plurality of curved profile shapes which are arranged in a repeating pattern across the radially inner surface region. None of the walls intersects with any other wall.
  • the curved profile shapes have no radii of curvature less than 0.5 mm.
  • an abradable sealing element for positioning radially outwardly of a plurality of aerofoil blades of a gas turbine engine, the abradable sealing element comprising:
  • the abradable sealing element By forming each repeating unit with a multi-lobed profile shape, the abradable sealing element has an increased perimetric length of inwardly projecting wall. This in turn increases the degree of abrasion that can be accommodated by the sealing element before maintenance or repair is required.
  • each repeating unit also increases the structural rigidity of the sealing element structure, which in turn increases its effectiveness at sealing against the plurality of aerofoil blades.
  • the guard wall surrounding each of the cooling holes prevents debris and/or wear particles from accumulating around the cooling holes, and which might otherwise restrict or block the hole.
  • the tubular geometry of the guard walls corresponds to the cross-sectional profile of the cooling holes.
  • the guard wall has the same cross-sectional geometry as the cooling hole. This has the effect of moving the exit aperture of a cooling flow through the cooling holes to the radially outward surface of the abradable sealing element.
  • a cooling hole is provided in each of the plurality of multi-lobed profile shapes.
  • Providing a cooling hole within each of the multi-lobed profile shapes enables a cooling air flow to pass over the walls of the profile shape to keep the walls cool.
  • each guard wall is provided with a perforated cover portion at a radially inward end thereof, the perforated cover portion extending completely across the radially inward end.
  • the perforated cover portion prevents blockage of the cooling hole by blown powder and sinter.
  • the perforations in the cover portion provide a diffusing action for the cooling flow through the holes during operational use of the sealing element.
  • each guard wall extends radially inwardly from the surface region to a first height.
  • Each of the guard walls has the same radially inward height as the wall structure, i.e. both the guard walls and the wall structure extend radially inwardly from the surface region to the first height.
  • the wall structure extends radially inwardly from the surface region to the first height.
  • the cooling air flow exhausting from the cooling hole can spill over the edge of the hole and into the centre region of each corresponding multi-lobed shape, even when the aerofoil blades are passing over the radially inwardly surfaces of the wall structure.
  • the walls further form one or more straight line boundaries at one or more edges of the radially inner surface region.
  • each of the curved portions has a radius of curvature greater than 0.5mm.
  • each of the curved portions with a radius of curvature greater than 0.5mm prevents debris and/or wear particles from agglomerating within the multi-lobed profile shape and thereby reducing the effectiveness of the abradable layer.
  • a build-up of debris and/or wear particles within the multi-lobed profile shape can result in increased heat generation due to increased friction and reduced cooling air flow.
  • the wall structure extends continuously from a boundary into a central region of the sealing element, around a plurality of concave and convex arcs and returning to the straight line boundary, the sum of the lengths of the concave arcs being substantially equal to the sum of the length of the convex arcs.
  • Forming the lengths of the concave arcs to be substantially equal to the sum of the length of the convex arcs provides for a substantially symmetrical wall structure geometry. This in turn makes the sealing element more easily packaged within the available space, and maximises the wall length.
  • the wall returns to the boundary adjacent to the point at which the wall leaves the boundary.
  • the walls are configured such that all the additive layers of each multi-lobed profile shape can be formed by moving the laser in a closed-circuit weld deposition path, without any reversal of laser direction, from a weld deposition start point to a weld deposition end point.
  • each of the additive layers making up the wall structure in a single pass makes the abradable sealing element easier and quicker to manufacture. Forming each additive layer in a single pass also makes the layer more robust and structurally stronger.
  • repeating units are bounded solely by the continuous wall and the radially inwardly facing surface of the sealing element.
  • a thickness of the walls reduces towards their radially inwardly facing edges.
  • the wall structure extends over substantially the whole of the radially inner surface region of the sealing element.
  • the spaces between adjacent ones of the repeating units, and the spaces between the wall structure and the guard walls are filled with an abradable material
  • Filling the spaces between adjacent ones of the repeating units with an abradable material increases the abrasion resistance of the sealing element and hence increase the service life of the sealing element.
  • the radially inwardly facing surface region completely encloses the plurality of aerofoil blades.
  • the abradable sealing element is formed in a single piece as a circular ring completely enclosing the plurality of aerofoil blades.
  • a seal segment ring for a turbine of a gas turbine engine, wherein the seal segment ring comprises a plurality of circumferentially arranged abradable sealing elements according to the first aspect.
  • a seal segment ring is formed from two or more abradable sealing elements, each sealing element being formed with a sector shaped geometry. This arrangement enables multiple smaller components to be used to form a seal segment ring.
  • This arrangement may be more convenient when the seal segment ring has a large diameter. This arrangement also makes repair and/or overhaul easier and quicker for a user.
  • a gas turbine engine comprising a turbine assembly, the turbine assembly comprising a seal segment ring according to the second aspect of the present invention.
  • a third aspect of the present invention there is provided a method of forming an abradable sealing element according to the first aspect, the method comprising the step of:
  • a scaffold structure provides mechanical support for features such as tubular walls.
  • a scaffold structure is inserted into each of the cooling holes in the surface region and as the blown powder is deposited onto the surface the scaffold maintains the geometry of the guard wall.
  • the method further comprises the step of: forming a perforated cover portion completely across a radially inward end of the guard wall.
  • the method further comprises the step of: removing the scaffold structure from each of the cooling holes.
  • the scaffold structure is formed from a material that is burned out during the sinter cycle.
  • all of the additive layers of each curved profile shape are formed by moving the laser in a closed-circuit weld deposition path, without any reversal of laser direction, from a weld deposition start point to a weld deposition end point.
  • aspects of the disclosure provide devices, methods and systems which include and/or implement some or all of the actions described herein.
  • the illustrative aspects of the disclosure are designed to solve one or more of the problems herein described and/or one or more other problems not discussed.
  • a turbofan gas turbine engine 108 as shown in Figure 1 , comprises in flow series an intake 11, a fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, an intermediate pressure turbine 17, a low pressure turbine 18 and an exhaust 19.
  • the fan assembly 12 comprises a plurality of circumferentially arranged aerofoil blades 106.
  • the high pressure turbine 16 is arranged to drive the high pressure compressor 14 via a first shaft 26.
  • the intermediate pressure turbine 17 is arranged to drive the intermediate pressure compressor 13 via a second shaft 28 and the low pressure turbine 18 is arranged to drive the fan 12 via a third shaft 30. In operation air flows into the intake 11 and is compressed by the fan 12.
  • a first portion of the air flows through, and is compressed by, the intermediate pressure compressor 13 and the high pressure compressor 14 and is supplied to the combustion chamber 15.
  • Fuel is injected into the combustion chamber 15 and is burnt in the air to produce hot exhaust gases which flow through, and drive, the high pressure turbine 16, the intermediate pressure turbine 17 and the low pressure turbine 18.
  • the hot exhaust gases leaving the low pressure turbine 18 flow through the exhaust 19 to provide propulsive thrust.
  • a second portion of the air bypasses the main engine to provide propulsive thrust.
  • Each of the high pressure turbine 16, the intermediate pressure turbine 17 and the low pressure turbine 18, comprises one or more turbine discs.
  • Each turbine disc comprises a plurality of turbine blades enclosed by an abradable sealing element 100.
  • the abradable sealing element provides a light rubbing seal between the radially distal edges of the turbine blades and the turbine housing.
  • an abradable sealing element according to an embodiment of the disclosure is designated generally by the reference numeral 100, the holder
  • the abradable sealing element 100 comprises a radially inwardly facing surface region 110 and a plurality of cooling holes 130.
  • the abradable sealing element 100 is formed as a sector of a larger circular geometry.
  • several abradable seal elements 100 are positioned together in a circumferentially contiguous arrangement to form a circular seal segment ring.
  • the abradable sealing element 100 may be formed a unitary circular component.
  • the radially inwardly facing surface region 110 comprises a wall structure 112.
  • the wall structure 112 has one or more radially inwardly projecting walls 114.
  • the radially inwardly projecting walls 114 are formed by additive layer, powder fed, laser weld deposition. In other words, the radially inwardly projecting walls 114 are formed from a plurality of individual wall layers 125.
  • each additive layer 125 can be formed by moving the laser in a closed-circuit weld deposition path, without any reversal of laser direction, from a weld deposition start point 170 to a weld deposition end point 172.
  • Each of the inwardly projecting walls 114 is continuous. Each of the inwardly projecting walls 114 has a wall thickness 115. Each of the inwardly projecting walls 114 has a first height 116 in a direction normal to, and extending from, the radially inwardly facing surface 110. Each of the inwardly projecting walls 114 defines a plurality of repeating units 120 arranged circumferentially around the radially inwardly facing surface region 110.
  • Each of the repeating units 120 is open at a radially inwardly facing side of the surface region 110.
  • Each repeating unit 120 comprises a plurality of curved portions 122 that together form a multi-lobed profile shape 124.
  • Each of the curved portions 122 has a radius of curvature 123.
  • the radius of curvature 123 is greater than 0.5mm.
  • the plurality of curved portions 122 comprises a plurality of concave arcs 126 and plurality of convex arcs 128.
  • the plurality of curved portions 122 comprises an alternating arrangement of concave arcs 126 and convex arcs 128.
  • the sum of the lengths of the concave arcs 126 is substantially equal to the sum of the length of the convex arcs 128.
  • Each cooling hole 130 is provided in the radially inwardly facing surface region 110 at a position 132 within the multi-lobed profile shape 124.
  • a cooling hole 130 is provided in each of the plurality of multi-lobed profile shapes 124.
  • a cooling hole 130 may be provided in alternate ones of the plurality of multi-lobed profile shapes 124.
  • a guard wall 140 is provided in the radially inwardly facing surface region 110 at a position concentric with a corresponding one of the cooling holes 130.
  • each cooling hole 130 is provided with a corresponding guard wall 140, with each guard wall 140 being concentric with the corresponding cooling hole 130.
  • Each guard wall 140 has a second height 142 in a direction normal to, and extending from, the radially inwardly facing surface 110.
  • the second height 142 is equal to the first height 116.
  • a scaffold structure 138 is inserted into each one of the cooling holes 130.
  • the use of scaffold structures 138 provides mechanical support for the deposited material.
  • Such scaffold structures 138 may take many different forms. In this arrangement, the scaffold structure 138 takes the form of a skeletal frame structure.
  • the multi-lobed profile shape 124 is arranged to extend axially across the radially inwardly facing surface region 110 from a straight line boundary 118.
  • the straight line boundary 118 lies in a plane normal to an axis of the turbine assembly.
  • the spaces 148 between adjacent ones of the repeating units 120 together with the spaces between the spaces between the wall structure and the guard walls are filled with an abradable material 150.
  • This abradable material 150 extends radially inwardly from the radially inwardly facing surface region 110 to the first height 116. In other words, a radially inwardly facing surface of the abradable material 150 is level with the inwardly projecting walls 114.
  • the sealing element 100 is sintered. During the sinter process, the scaffold structure 138 is burned out of the internal volume of the guard wall 140.

Claims (13)

  1. Abschabbare Dichtungsstruktur (100) zum radial äußeren Positionieren einer Vielzahl von Stromlinienschaufeln (106) eines Gasturbinenmotors (108), wobei die abschabbare Dichtungsstruktur (100) umfasst:
    eine radial nach innen zeigende Oberflächenregion (110);
    und wobei die radial nach innen zeigende Oberflächenregion (110) eine Wandstruktur (112) umfasst, wobei die Wandstruktur (112) eine oder mehrere radial nach innen vorstehende Wände (114) aufweist, die durch Laserschweißablagerung mit pulvergespeisten additiven Schichten geformt werden; wobei jede der nach innen vorstehenden Wände (114) durchgängig ist und eine Vielzahl von sich wiederholenden Einheiten (120) definiert, die in Umfangsrichtung um die radial nach innen zeigende Oberflächenregion (110) angeordnet sind, wobei jede sich wiederholende Einheit (120) an einer radial nach innen zeigenden Seite der Dichtungsstruktur (100) offen ist, wobei jede sich wiederholende Einheit (120) eine Vielzahl gekrümmter Abschnitte (122) umfasst, die eine mehrlappige Profilform (124) formen, dadurch gekennzeichnet, dass die abschabbare Dichtungsstruktur (100) ferner eine Vielzahl von Kühlungslöchern (130) umfasst und jedes Kühlungsloch (130) in der radial nach innen zeigenden Oberflächenregion (110) an einer Position in der mehrlappigen Profilform (124) bereitgestellt ist und dass eine Vielzahl rohrförmiger Schutzwände (140) in der radial nach innen zeigenden Oberflächenregion (110) bereitgestellt ist und sich radial nach innen davon erstrecken, wobei jede Schutzwand (140) an einer zu einem entsprechenden oder jedem Kühlungsloch (130) konzentrischen Position und beabstandet von der Wandstruktur (112) positioniert ist.
  2. Abschabbare Dichtungsstruktur (100) nach Anspruch 1, wobei ein Kühlungsloch (130) in jeder der Vielzahl mehrlappiger Profilformen (124) bereitgestellt ist.
  3. Abschabbare Dichtungsstruktur (100) nach Anspruch 1, wobei jede Schutzwand (140) mit einem perforierten Abdeckungsabschnitt an einem radial inneren Ende davon bereitgestellt ist, wobei sich der perforierte Abdeckungsabschnitt vollständig über das radial innere Ende erstreckt.
  4. Abschabbare Dichtungsstruktur nach einem der Ansprüche 1 bis 3, wobei die Wände (114) ferner eine oder mehrere geradlinige Grenzen (118) an einer oder mehreren Kanten der radial inneren Oberflächenregion (110) formen.
  5. Abschabbare Dichtungsstruktur nach einem der Ansprüche 1 bis 4, wobei jeder der gekrümmten Abschnitte (122) einen Krümmungsradius (123) von mehr als 0,5 mm aufweist.
  6. Abschabbare Dichtungsstruktur nach einem der Ansprüche 1 bis 5, wobei sich die Wandstruktur (112) durchgängig von einer Grenze (118) in eine zentrale Region der Dichtungsstruktur (100), um eine Vielzahl konkaver und konvexer Bögen (126:128) erstreckt und zur geradlinigen Grenze (118) zurückkehrt, wobei die Summe der Längen der konkaven Bögen (126) im Wesentlichen gleich der Summe der Länge der konvexen Bögen (128) ist.
  7. Abschabbare Dichtungsstruktur nach Anspruch 6, wobei die Wand (114) angrenzend an den Punkt, an dem die Wand (114) die Grenze (118) verlässt, zur Grenze (118) zurückkehrt.
  8. Abschabbare Dichtungsstruktur (100) nach einem der Ansprüche 1 bis 7, wobei sich eine Dicke (115) der Wände (114) zu ihren radial nach innen zeigenden Kanten (111) verringert.
  9. Abschabbare Dichtungsstruktur (100) nach einem der Ansprüche 1 bis 8, wobei die Räume zwischen angrenzenden der sich wiederholenden Einheiten (120) und die Räume zwischen der Wandstruktur (112) und den Schutzwänden (140) mit einem abschabbaren Material (150) gefüllt sind.
  10. Dichtungssegmentring (160) für eine Turbine eines Gasturbinenmotors (108), wobei der Dichtungssegmentring (160) eine Vielzahl von in Umfangsrichtung angeordneten abschabbaren Dichtungselementen (100) nach einem der Ansprüche 1 bis 9 umfasst.
  11. Verfahren zum Formen einer abschabbaren Dichtungsstruktur (100) nach einem der Ansprüche 1 bis 9, wobei das Verfahren die folgenden Schritte umfasst:
    Formen der Wandstruktur (112) an der radial nach innen zeigenden Oberflächenregion (110) der abschabbaren Dichtungsstruktur (100) durch Laserschweißablagerung mit pulvergespeisten additiven Schichten;
    und Formen der Vielzahl von Kühlungslöchern (130), wobei jedes Kühlungsloch (130) in der radial nach innen zeigenden Oberflächenregion (110) an einer Position in einer jeweiligen der mehrlappigen Profilformen (124) bereitgestellt ist, Einführen einer Gerüststruktur (138) in jedes der Kühlungslöcher (130) und Formen der Vielzahl von Schutzwänden (140) in der radial nach innen zeigenden Oberflächenregion (110), wobei jede Schutzwand (140) an einer Position, die konzentrisch zu einem entsprechenden der Kühlungslöcher (130) ist, positioniert ist, und jede Schutzwand (140) um eine entsprechende der Gerüststrukturen (138) geformt ist.
  12. Verfahren nach Anspruch 11, ferner umfassend die folgenden Schritte:
    Formen eines perforierten Abdeckungsabschnitts vollständig über ein radial inneres Ende der Schutzwand (140).
  13. Verfahren nach Anspruch 12, ferner umfassend die folgenden Schritte:
    Entfernen der Gerüststruktur (138) aus jedem der Kühlungslöcher (130).
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GB201916958D0 (en) * 2019-11-21 2020-01-08 Rolls Royce Plc Abradable sealing element

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EP2818645A1 (de) * 2013-06-27 2014-12-31 Rolls-Royce plc Abreibbare Auskleidung für einen Gasturbinenmotor

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US3365172A (en) * 1966-11-02 1968-01-23 Gen Electric Air cooled shroud seal
US4618152A (en) * 1983-01-13 1986-10-21 Thomas P. Mahoney Honeycomb seal structure
US5161942A (en) * 1990-10-24 1992-11-10 Westinghouse Electric Corp. Moisture drainage of honeycomb seals
US6155778A (en) * 1998-12-30 2000-12-05 General Electric Company Recessed turbine shroud
GB201103176D0 (en) * 2011-02-24 2011-04-06 Rolls Royce Plc Endwall component for a turbine stage of a gas turbine engine
GB201205663D0 (en) * 2012-03-30 2012-05-16 Rolls Royce Plc Effusion cooled shroud segment with an abradable system
US9702375B2 (en) * 2013-07-16 2017-07-11 United Technologies Corporation Liner attaching scheme
US9845731B2 (en) * 2014-09-24 2017-12-19 United Technologies Corporation Self-modulated cooling on turbine components
GB201417307D0 (en) * 2014-10-01 2014-11-12 Rolls Royce Plc Sealing element
EP3130827B1 (de) * 2015-08-14 2019-10-02 Goodrich Actuation Systems Limited Dichtungen

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EP2818645A1 (de) * 2013-06-27 2014-12-31 Rolls-Royce plc Abreibbare Auskleidung für einen Gasturbinenmotor

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